Flow sleeve for a combustion module of a gas turbine

ABSTRACT

A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.

FIELD OF THE INVENTION

The present invention generally involves a combustor for a gas turbine.More specifically, the invention relates to a flow sleeve for acombustion module of the combustor.

BACKGROUND OF THE INVENTION

A combustion section of a gas turbine generally includes a plurality ofcombustors that are arranged in an annular array around an outer casingsuch as a compressor discharge casing. Pressurized air flows from acompressor to the compressor discharge casing and is routed to eachcombustor. Fuel from a fuel nozzle is mixed with the pressurized air ineach combustor to form a combustible mixture within a primary combustionzone of the combustor. The combustible mixture is burned to produce hotcombustion gases having a high pressure and high velocity.

In a typical combustor, the combustion gases are routed towards an inletof a turbine of the gas turbine through a hot gas path that is at leastpartially defined by an annular combustion liner and an annulartransition duct that extends downstream from the combustion liner andterminates at the inlet to the turbine. Thermal and kinetic energy aretransferred from the combustion gases to the turbine to cause theturbine to rotate, thereby producing mechanical work. For example, theturbine may be coupled to a shaft that drives a generator to produceelectricity.

In particular combustors, a combustion module is utilized to inject agenerally lean fuel-air mixture into the hot gas path downstream fromthe primary combustion zone. The combustion module generally includes anannular fuel distribution manifold that circumferentially surrounds aportion of a cap assembly that partially surrounds the fuel nozzle, anda fuel injection assembly that extends between the fuel distributionmanifold and the inlet to the gas turbine. The fuel injection assemblyincludes an annular combustion liner that extends continuously betweenthe cap assembly and the inlet to the turbine. The continuouslyextending combustion liner defines the hot gas path within thecombustor, thereby eliminating the separate transition duct. Thecombustion liner includes an annular main body that comprises of aconical section having a substantially circular cross section and atransition section that extends downstream from the conical section andthat has a substantially non-circular cross section. The fuel injectionassembly further includes a plurality of radially extending fuelinjectors, also known as late lean fuel injectors that inject the leanfuel-air combustible mixture into the hot gas path downstream from theprimary combustion zone. As a result, the combustion gas temperature isincreased and the thermodynamic efficiency of the combustor is improvedwithout producing a corresponding increase in the production ofundesirable emissions such as oxides of nitrogen (NO_(X)). However, theincrease in the temperature of the combustion gases results in anincrease of thermal stresses on the combustion liner.

One technique for cooling the combustion liner of the combustion moduleincludes surrounding the combustion liner with a flow sleeve assembly soas to define a cooling flow passage therebetween, and routing a portionof the compressed working fluid through the cooling passage to provideat least one of impingement, convective or conductive cooling to thecombustion liner. The flow sleeve assembly generally includes an annularsupport sleeve that surrounds a forward end portion of the combustionliner and that is positioned concentrically within the fuel distributionmanifold, an annular flow sleeve that is coupled to an aft end of thesupport sleeve and that surrounds the conical section of the combustionliner, and an annular impingement sleeve that is coupled to an aft endof the flow sleeve and that surrounds the transition section of thecombustion liner.

While the flow sleeve assembly is generally effective for cooling thecombustion liner, the multiple connections between the variouscomponents may leak or develop leaks over time due to tolerance issuesand/or due to thermal and/or mechanical cycle fatigue, thereby impactingthe overall cooling effectiveness and durability of the flow sleeveassembly. In addition, the loss of the compressed working fluid from thecooling passage may result in a decrease of combustor performance due toa decrease in the amount of the compressed working fluid that is routedto the fuel nozzle for combustion. Furthermore, the multiple componentsincrease time and costs associated with assembly, disassembly and themanufacture of the combustion module. Therefore, an improved system forcooling the combustion liner of the combustion module would be useful.

BRIEF DESCRIPTION OF THE INVENTION

Aspects and advantages of the invention are set forth below in thefollowing description, or may be obvious from the description, or may belearned through practice of the invention.

One embodiment of the present invention is a combustion module for acombustor of a gas turbine that includes an annular fuel distributionmanifold disposed at an upstream end of the combustion module. The fueldistribution manifold includes an annular support sleeve having an innersurface. The combustion module further includes a fuel injectionassembly having an annular combustion liner that extends downstream fromthe fuel distribution manifold and that terminates at an aft frame, andan annular flow sleeve that circumferentially surrounds the combustionliner. The flow sleeve extends downstream from the fuel distributionmanifold and terminates at the aft frame. The flow sleeve extendscontinuously between the support sleeve and the aft frame. A forwardportion of the flow sleeve is positioned concentrically within thesupport sleeve where the forward portion is slidingly engaged with theinner surface of the support sleeve.

Another embodiment of the present invention is a combustor. Thecombustor includes an end cover that is coupled to an outer casing thatsurrounds the combustor, an axially extending fuel nozzle that extendsdownstream from the end cover, an annular cap assembly that extendsradially and axially within the combustor where the cap assembly atleast partially surrounds the fuel nozzle, and a combustion modulehaving an annular fuel distribution manifold that circumferentiallysurrounds at least a portion of the cap assembly. The combustion modulefurther includes a fuel injection assembly that extends downstream fromthe fuel distribution manifold. The fuel injection assembly includes anannular combustion liner that extends downstream from the cap assemblyand that terminates at an aft frame, and an annular flow sleeve thatsurrounds the combustion liner. The flow sleeve includes a forwardportion that is positioned concentrically within the fuel distributionmanifold, and an aft end that is coupled to the aft frame. The flowsleeve extends continuously between the forward portion of the flowsleeve and the aft frame.

The present invention may also include a gas turbine. The gas turbinegenerally includes a compressor, a compressor discharge casing disposeddownstream from the compressor and a turbine disposed downstream fromthe compressor discharge casing. A combustor extends at least partiallythrough the compressor discharge casing. The combustor includes an endcover that is coupled to the compressor discharge casing, an axiallyextending fuel nozzle that extends downstream from the end cover, anannular cap assembly that is disposed downstream from the end cover andthat at least partially surrounds the fuel nozzle, and a combustionmodule that extends downstream from the cap assembly. The combustionmodule includes an annular fuel distribution manifold thatcircumferentially surrounds at least a portion of the cap assembly. Thefuel distribution manifold includes a radially extending mounting flangethat is coupled to the compressor discharge casing and an axiallyextending annular support sleeve that includes an inner surface. Thecombustion module further includes a fuel injection assembly thatextends downstream from the fuel distribution manifold. The fuelinjection assembly includes an annular combustion liner that extendsdownstream from the cap assembly and terminates at an aft frame. Anannular flow sleeve surrounds the combustion liner and a plurality offuel injectors extend through the flow sleeve and the combustion linerdownstream from the cap assembly. The fuel injectors are fluidlyconnected to the fuel distribution manifold. The flow sleeve includes aforward portion that is positioned concentrically within the supportsleeve between the combustion liner and the inner surface of the supportsleeve and an aft end that is coupled to the aft frame. The flow sleeveextends continuously between the forward portion of the flow sleeve andthe aft frame.

Those of ordinary skill in the art will better appreciate the featuresand aspects of such embodiments, and others, upon review of thespecification.

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of the present invention, including thebest mode thereof to one skilled in the art, is set forth moreparticularly in the remainder of the specification, including referenceto the accompanying figures, in which:

FIG. 1 is a functional block diagram of an exemplary gas turbine withinthe scope of the present invention;

FIG. 2 is a cross sectional side view of a portion of an exemplary gasturbine, including an exemplary combustor that encompasses variousembodiments of the present invention;

FIG. 3 is a perspective view of a combustion module as shown in FIG. 2,that may encompass various embodiments of the present invention;

FIG. 4 is an exploded perspective view of the combustion module as shownin FIG. 3, according to one embodiment of the present invention;

FIG. 5 is a cross sectional side view of the combustion module as showin FIG. 3, according to one embodiment of the present invention;

FIG. 6 is a side view of a combustion liner of the combustion module asshown in FIG. 3, according to at least one embodiment of the presentinvention; and

FIG. 7 is an enlarged cross sectional view of a portion of the combustorincluding a portion of the combustion module as shown in FIG. 2.

DETAILED DESCRIPTION OF THE INVENTION

Reference will now be made in detail to present embodiments of theinvention, one or more examples of which are illustrated in theaccompanying drawings. The detailed description uses numerical andletter designations to refer to features in the drawings. Like orsimilar designations in the drawings and description have been used torefer to like or similar parts of the invention. As used herein, theterms “first”, “second”, and “third” may be used interchangeably todistinguish one component from another and are not intended to signifylocation or importance of the individual components. The terms“upstream” and “downstream” refer to the relative direction with respectto fluid flow in a fluid pathway. For example, “upstream” refers to thedirection from which the fluid flows, and “downstream” refers to thedirection to which the fluid flows. The term “radially” refers to therelative direction that is substantially perpendicular to an axialcenterline of a particular component, and the term “axially” refers tothe relative direction that is substantially parallel to an axialcenterline of a particular component.

Each example is provided by way of explanation of the invention, notlimitation of the invention. In fact, it will be apparent to thoseskilled in the art that modifications and variations can be made in thepresent invention without departing from the scope or spirit thereof.For instance, features illustrated or described as part of oneembodiment may be used on another embodiment to yield a still furtherembodiment. Thus, it is intended that the present invention covers suchmodifications and variations as come within the scope of the appendedclaims and their equivalents. Although exemplary embodiments of thepresent invention will be described generally in the context of acombustor incorporated into a gas turbine for purposes of illustration,one of ordinary skill in the art will readily appreciate thatembodiments of the present invention may be applied to any combustorincorporated into any turbomachine and is not limited to a gas turbinecombustor unless specifically recited in the claims.

Referring now to the drawings, wherein identical numerals indicate thesame elements throughout the figures, FIG. 1 provides a functional blockdiagram of an exemplary gas turbine 10 that may incorporate variousembodiments of the present invention. As shown, the gas turbine 10generally includes an inlet section 12 that may include a series offilters, cooling coils, moisture separators, and/or other devices topurify and otherwise condition a working fluid (e.g., air) 14 enteringthe gas turbine 10. The working fluid 14 flows to a compressor sectionwhere a compressor 16 progressively imparts kinetic energy to theworking fluid 14 to produce a compressed working fluid 18 at a highlyenergized state.

The compressed working fluid 18 is mixed with a fuel 20 from a fuelsupply 22 to form a combustible mixture within one or more combustors24. The combustible mixture is burned to produce combustion gases 26having a high temperature and pressure. The combustion gases 26 flowthrough a turbine 28 of a turbine section to produce work. For example,the turbine 28 may be connected to a shaft 30 so that rotation of theturbine 28 drives the compressor 16 to produce the compressed workingfluid 18. Alternately or in addition, the shaft 30 may connect theturbine 28 to a generator 32 for producing electricity. Exhaust gases 34from the turbine 28 flow through an exhaust section 36 that connects theturbine 28 to an exhaust stack 38 downstream from the turbine 28. Theexhaust section 36 may include, for example, a heat recovery steamgenerator (not shown) for cleaning and extracting additional heat fromthe exhaust gases 34 prior to release to the environment.

FIG. 2 provides a cross sectional side view of a portion of an exemplarygas turbine 10 including an exemplary combustor 50 that may encompassvarious embodiments of the present disclosure. As shown, the combustor50 is at least partially surrounded by an outer casing 52 such as acompressor discharge casing 54 that is disposed downstream from thecompressor and/or an outer turbine casing 56. The outer casing 52 is influid communication with the compressor 16 and at least partiallydefines a high pressure plenum 58 that surrounds at least a portion ofthe combustor 50. An end cover 60 is coupled to the outer casing 52 atone end of the combustor 50.

As shown in FIG. 2, the combustor 50 generally includes at least oneaxially extending fuel nozzle 62 that extends downstream from the endcover 60, an annular cap assembly 64 that extends radially and axiallywithin the outer casing 52 downstream from the end cover 60, an annularhot gas path duct or combustion liner 66 that extends downstream fromthe cap assembly 64 and an annular flow sleeve 68 that surrounds atleast a portion of the combustion liner 66. The combustion liner 66defines a hot gas path 70 for routing the combustion gases 26 throughthe combustor 50. The end cover 60 and the cap assembly 64 at leastpartially define a head end 72 of the combustor 50.

The cap assembly 64 generally includes a forward end 74 that is positiondownstream from the end cover 60, an aft end 76 that is disposeddownstream from the forward end 74, and one or more annular shrouds 78that extend at least partially therebetween. In particular embodiments,the axially extending fuel nozzle(s) 62 extend at least partiallythrough the cap assembly 64 to provide a first combustible mixture 80that consists primarily of the fuel 20 (FIG. 1) and a portion of thecompressed working fluid 18 from the compressor 16 to a primarycombustion zone 82 that is defined within the combustion liner 66downstream from the aft end 76 of the cap assembly 64.

In particular embodiments, the combustor 50 further includes one or moreradially extending fuel injectors 84 also known as late-lean fuelinjectors that extend through the flow sleeve 68 and the combustionliner 66 at a point that is downstream from the at least one axiallyextending fuel nozzle 62. The combustion liner 66 defines a combustionchamber 86 within the combustor 50. In particular embodiments, thecombustion liner 66 further defines a secondary combustion zone 88 thatis proximate to the fuel injector(s) 84 and downstream from the primarycombustion zone 82. In particular embodiments, the combustion liner 66,the flow sleeve 68 and the fuel injector(s) 84 are provided as part of acombustion module 100 that extends through the outer casing 52 and thatcircumferentially surrounds at least a portion of the cap assembly 64.

FIG. 3 provides a perspective view of the combustion module 100 as shownin FIG. 2, and FIG. 4 provides an exploded perspective view of thecombustion module 100 as shown in FIG. 3. As shown in FIG. 3, thecombustion module 100 is generally provided as an assembled or singularcomponent. The combustion module 100 includes a forward or upstream end102 that is axially separated from an aft or downstream end 104 withrespect to an axial centerline 106 of the combustion module 100.

In particular embodiments, as shown in FIG. 4, the combustion module 100includes an annular fuel distribution manifold 108 disposed at theupstream end 102 of the combustion module 100 and a fuel injectionassembly 110 that extends downstream from the fuel distribution manifold108 and that terminates at the downstream end 104 of the combustionmodule 100. The fuel distribution manifold 108 includes a radiallyextending mounting flange 112 that extends circumferentially around aforward end 114 of the fuel distribution manifold 108. As shown in FIG.2, the mounting flange 112 at least partially defines a fuel plenum 116.As shown in FIGS. 2 and 4, a fuel inlet port 118 extends outward fromthe mounting flange 112. The fuel inlet port 118 provides for fluidcommunication between the fuel supply 22 (FIG. 1) and the fuel plenum116 (FIG. 2). As shown in FIG. 4, the fuel distribution manifold 108further includes an annular support sleeve 120 having an inner side 122that is radially separated from an outer side 124. The annular supportsleeve 120 extends generally axially downstream from the mounting flange112.

In particular embodiments, as shown in FIG. 4, the combustion liner 66,the flow sleeve 68 and the fuel injector(s) 84 are included as part ofthe fuel injection assembly 110. As shown in FIG. 3, each fuel injector84 may be fluidly coupled to the fuel distribution manifold 108 througha fluid conduit 126 that extends between the fuel injector 84 and themounting flange 112.

FIG. 5 provides a cross sectional side view of the combustion module 100as shown in FIGS. 2, 3 and 4, and FIG. 6 provides a side view of thecombustion liner 66 of the combustion module 100. As shown in FIG. 5,the combustion liner 66 extends downstream from the fuel distributionmanifold 108 and an aft or downstream end 128 of the combustion liner 66terminates at an aft frame 130 or other support structure thatcircumferentially surrounds the aft end 128 as shown in FIG. 3. As shownin FIG. 3, a mounting bracket 131 may be coupled to the aft frame 130.In one embodiment, as shown in FIG. 2, the aft frame 130 and/or themounting bracket 131 is coupled to the outer turbine casing 56 and themounting flange 112 of the fuel distribution manifold 108 is connectedto the compressor discharge casing 54 so as to constrain the combustionmodule 100 at both the forward and aft ends 102, 104 of the combustionmodule 100.

As shown in FIG. 6, the combustion liner 66 comprises an annular mainbody 132. The main body 132 generally includes a forward end 134 axiallyseparated from an aft end 136 with respect to an axial centerline 138 ofthe combustion liner 66. The main body 132 extends continuously from theforward end 134 to the aft end 136. The main body 132 includes an outeror cold side 140 that extends between the forward end 134 and the aftend 136. In particular embodiments, as shown in FIGS. 3 and 6, aplurality of cooling features 142 such as raised ribs or turbulatorsextend radially outward from the outer surface 140 of the main body 132.

In particular embodiments, as shown in FIG. 6, the main body 132comprises a conical section 144 and a transition section 146, therebyeliminating the need for a separate transition duct. A transitionalintersection 148 is defined between the forward end 134 and the aft end136 of the main body 132 at a point where the conical section 144 andthe transition section 146 intersect. For example, where the main body132 begins to change from a generally circular cross section to anon-circular cross section. In particular embodiments, an annular flange150 is disposed at the forward end 132 of the main body 132. The flange150 at least partially surrounds a portion of the cap assembly 64 (FIG.2). In particular embodiments, as shown in FIG. 6, the cooling features142 may be disposed on the conical section 144 and/or the transitionsection 146 of the main body 132.

As shown in FIGS. 4 and 5, the flow sleeve 68 includes a forward end 152and an outer forward portion 154 disposed proximate to the forward end152 and an aft end 156 that is axially separated from the forward end152 with respect to the axial centerline 106 (FIG. 5) of the combustionmodule 100. The forward portion 154 of the flow sleeve 68 may at leastpartially define an outer engagement surface 158. In particularembodiments, as shown in FIG. 5, the flow sleeve 68 extends continuouslybetween the fuel distribution manifold 108 and the aft frame 130. Inparticular embodiments, as shown in FIG. 5, the forward portion 154 ofthe flow sleeve 68 is positioned generally concentrically within thesupport sleeve 120 of the fuel distribution manifold 108.

FIG. 7 provides an enlarged view of a portion of the combustor 50including a portion of the cap assembly 64 and a portion of thecombustion module 100 as shown in FIG. 2. In particular embodiments, asshown in FIG. 7, the outer engagement surface 158 of the forward portion154 of the flow sleeve 68 is slidingly engaged with the inner surface122 of the support sleeve 120. In this manner, the flow sleeve 68 isallowed to slide or translate along the inner side 122 of the supportsleeve 120 of the fuel distribution manifold 108 during operation of thecombustor 24. As further shown in FIG. 7, the flange 150 of the mainbody 132 of the combustion liner 66 at least partially surrounds aportion of the cap assembly 64.

In particular embodiments, as shown in FIG. 7, a compression or springseal 162 such as a hula seal extends radially between the outerengagement surface 158 of the forward portion 154 of the flow sleeve 68and the inner side 122 of the support sleeve 120. In particularembodiments, the spring seal 162 may be connected to the support sleeve120. In the alternative, the spring seal 162 may be connected to theflow sleeve 68. The spring seal 162 at least partially providesstructural support for the flow sleeve 68 during installation and/oroperation of the gas turbine 10 while allowing for axial movementbetween the fuel distribution manifold 108 and the fuel injectionassembly 110 during various operational modes of the gas turbine 10 suchas during startup, shutdown and/or turndown operations.

In particular embodiments, as shown in FIG. 5, the flow sleeve 68 isradially separated from the combustion liner 66 so as to define anannular cooling flow passage 164 therebetween. The cooling flow passage164 generally extends continuously along the length of the combustionliner 66. For example, the cooling flow passage 164 extends continuouslybetween the aft frame 130 and the forward portion 154 and/or the forwardend 152 of the flow sleeve 68.

In particular embodiments, as shown in FIG. 4, the flow sleeve 68 maycomprise a plurality of cooling or impingement holes 166 that providefor fluid communication through the flow sleeve 68 into the cooling flowpassage 164 (FIG. 5) during operation of the gas turbine 10. In at leastone embodiment, as shown in FIGS. 3 and 4, the flow sleeve 68 includestwo semi-annular flow sleeve sections 168 that wrap at least partiallyaround the combustion liner 66 (FIG. 5). As shown in FIG. 3, the twosemi-annular flow sleeve sections 168 are joined together using aplurality of fasteners 170 such as bolts or other locking fastenerswhich are suitable for the operating environment of the combustionmodule 100. In the alternative, the semi-annular flow sleeve sections168 may be welded or joined together by any mechanical means suitablefor the operating environment within the combustor 50.

In one embodiment, as shown in FIG. 5, the flow sleeve 68 is radiallyseparated from the combustion liner 66 at a radial distance 172 that isgenerally constant between the aft frame and the forward end 152 of themain body 132 of the combustion liner 66. In another embodiment, theradial distance 172 between the combustion liner 66 and the flow sleeve68 varies along/across the cold side 140 of the main body 132 of thecombustion liner 66. For example, the radial distance 172 may increaseand/or decrease across the conical section 144 and/or the transitionsection 146 of the combustion liner 66 to control a flow rate and/orvelocity of the compressed working fluid 18 (FIG. 2) at a particularlocation on the main body 132 as it flows through the cooling flowpassage 164, thereby allowing for enhanced localized control over thecooling effectiveness of the compressed working fluid 18 in particularareas of the cooling flow passage 164.

In particular embodiments, the flow sleeve 68 is separated from thecombustion liner 64 at a first radial distance 174 with respect to theconical section 144 and a second radial distance 176 with respect to thetransition section 146. In particular embodiments, the first radialdistance 174 is greater than the second radial distance 176 along atleast a portion of the conical section 144 of the combustion liner 66,thereby providing for effective impingement cooling at the transitionsection 146 of the main body 132 of the combustion liner 66 whilereducing a pressure drop of the compressed working fluid as it flowsfrom the high pressure plenum 58, through the cooling holes 166, intothe cooling flow passage 164 and onto the cold side 140 of the main body132. In the alternative, the second radial distance 176 may be greaterthan the first radial distance 168 along at least a portion of thetransition section 146 of the combustion liner 66 to control a flowvelocity of the compressed working fluid 18 through the cooling flowpassage 164 across the conical section 144 of the main body 132 of thecombustion liner 66.

In operation, as described above and as illustrated in the variousfigures, a portion of the compressed working fluid 18 from thecompressor 16 is routed into the cooling flow passage 164 through theplurality of cooling or impingement holes 166. The compressed workingfluid 18 is focused onto the outer or cold side 140 of the combustionliner 66 at the transition section 146 to provide impingement or jetcooling to the transition section 146 of the main body 132 of thecombustion liner 66. The radial distance 172 between the flow sleeve 68and the conical section 144 and/or the transition section 146 of thecombustion liner 66 is set as a constant distance and/or a varyingradial distance to control the flow volume and/or velocities of thecompressed working fluid 18 through the cooling flow passage 164,thereby effectively cooling the combustion liner, particularly at hotspots formed by increased combustion temperatures caused by late-leanfuel injection.

The compressed working fluid 18 provides at least one of impingement,convective or conductive cooling to the combustion liner 66 as it isrouted through the cooling flow passage 164 and on towards the head end58 of the combustor 50. The continuously extending flow sleeve 68eliminates any of the connection joints of previous flow sleeveassemblies. As a result, leakage from the cooling flow passage iseliminated, thereby improving the overall efficiency of the combustor50. In addition, by eliminating the multiple components of existing flowsleeve assemblies, the time and costs associated with assembly,disassembly and manufacture of the combustion module 100 are decreased.

This written description uses examples to disclose the invention,including the best mode, and also to enable any person skilled in theart to practice the invention, including making and using any devices orsystems and performing any incorporated methods. The patentable scope ofthe invention is defined by the claims, and may include other examplesthat occur to those skilled in the art. Such other examples are intendedto be within the scope of the claims if they include structural elementsthat do not differ from the literal language of the claims, or if theyinclude equivalent structural elements with insubstantial differencesfrom the literal language of the claims.

What is claimed is:
 1. A combustion module for a combustor of a gasturbine, comprising: a. an annular fuel distribution manifold disposedat an upstream end of the combustion module, the fuel distributionmanifold including an annular support sleeve having an inner surface; b.a fuel injection assembly having an annular combustion liner thatextends downstream from the fuel distribution manifold and thatterminates at an aft frame, and an annular flow sleeve thatcircumferentially surrounds the combustion liner, the flow sleeveextending downstream from the fuel distribution manifold and terminatingat the aft frame, the flow sleeve extending continuously between thesupport sleeve and the aft frame; and c. wherein a forward portion ofthe flow sleeve is positioned concentrically within the support sleevesuch that the fuel distribution manifold forms an annulus around theforward portion of the flow sleeve, the forward portion being slidinglyengaged with the inner surface of the support sleeve.
 2. The combustionmodule as in claim 1, further comprising a continuous cooling flowpassage defined between the combustion liner and the flow sleeve thatextends between the aft frame and the forward portion of the flowsleeve.
 3. The combustion module as in claim 1, wherein the combustionliner comprises a conical section and a transition section, the flowsleeve being radially separated from the combustion liner at a firstradial distance with respect to the conical section and a second radialdistance with respect to the transition section.
 4. The combustionmodule as in claim 1, wherein the flow sleeve is radially separated fromthe combustion liner at a radial distance that varies along the lengthof the combustion liner.
 5. The combustion module as in claim 1, whereinthe flow sleeve at least partially defines a plurality of impingementcooling passages.
 6. The combustion module as in claim 1, wherein thefuel injection assembly further comprises a plurality of fuel injectorsthat extend through the flow sleeve and the combustion liner so as toprovide for fluid communication into the combustion liner, each of thefuel injectors being fluidly connected to the fuel distributionmanifold.
 7. The combustion module as in claim 1, wherein the flowsleeve comprises of two or more semi-annular flow sleeve sections joinedtogether to surround the combustion liner.
 8. The combustion module asin claim 1, further comprising a compression seal that extends radiallybetween the forward portion of the flow sleeve and the inner surface ofthe support sleeve.
 9. A combustor comprising: a. an end cover coupledto an outer casing that surrounds the combustor; b. an axially extendingfuel nozzle that extends downstream from the end cover; c. an annularcap assembly that extends radially and axially within the combustor, thecap assembly at least partially surrounding the fuel nozzle; and d. acombustion module having an annular fuel distribution manifold thatcircumferentially surrounds at least a portion of the cap assembly and afuel injection assembly that extends downstream from the fueldistribution manifold, wherein the annular fuel distribution manifold ismounted between the end cover and the outer casing, the fuel injectionassembly comprising: i. an annular combustion liner that extendsdownstream from the cap assembly and that terminates at an aft frame;and ii. an annular flow sleeve that surrounds the combustion liner, theflow sleeve having a forward portion positioned concentrically withinthe fuel distribution manifold and an aft end coupled to the aft frame,wherein the fuel distribution manifold forms an annulus around theforward portion of the flow sleeve, and wherein the flow sleeve extendscontinuously between the forward portion and the aft frame.
 10. Thecombustor as in claim 9, further comprising a continuous cooling flowpassage defined between the combustion liner and the flow sleeve thatextends between the aft frame and the forward portion of the flowsleeve.
 11. The combustor as in claim 9, wherein the combustion linercomprises a conical section and a transition section, the flow sleevebeing radially separated from the combustion liner at a first radialdistance with respect to the conical section and a second radialdistance with respect to the transition section.
 12. The combustor as inclaim 9, wherein the flow sleeve is radially separated from thecombustion liner at a radial distance that varies along the length ofthe combustion liner.
 13. The combustor as in claim 9, wherein the flowsleeve at least partially defines a plurality of impingement coolingpassages.
 14. The combustor as in claim 9, wherein the fuel injectionassembly further comprises a plurality of fuel injectors that extendthrough the flow sleeve and the combustion liner so as to provide forfluid communication into the combustion liner downstream from the fuelnozzle, each of the fuel injectors being fluidly connected to the fueldistribution manifold.
 15. The combustor as in claim 9, wherein the flowsleeve comprises of two or more semi-annular flow sleeve sections joinedtogether to surround the combustion liner.
 16. The combustor as in claim9, further comprising a compression seal that extends radially betweenthe forward portion of the flow sleeve and the fuel distributionmanifold.
 17. A gas turbine, comprising: a. a compressor, a compressordischarge casing disposed downstream from the compressor and a turbinedisposed downstream from the compressor discharge casing; and b. acombustor that extends at least partially through the compressordischarge casing, the combustor having an end cover coupled to thecompressor discharge casing, an axially extending fuel nozzle thatextends downstream from the end cover, an annular cap assembly disposeddownstream from the end cover and that at least partially surrounds thefuel nozzle, and a combustion module that extends downstream from thecap assembly, the combustion module comprising: i. an annular fueldistribution manifold that circumferentially surrounds at least aportion of the cap assembly, the fuel distribution manifold having aradially extending mounting flange that is coupled to the compressordischarge casing and an axially extending annular support sleeve, thesupport sleeve having an inner surface, wherein the end cover is axiallyspaced from the compressor discharge casing via the radially extendingmounting flange; ii. a fuel injection assembly that extends downstreamfrom the fuel distribution manifold, the fuel injection assembly havingan annular combustion liner that extends downstream from the capassembly and terminates at an aft frame, an annular flow sleeve thatsurrounds the combustion liner, and a plurality of fuel injectors thatextend through the flow sleeve and the combustion liner downstream fromthe cap assembly, the fuel injectors being fluidly connected to the fueldistribution manifold; and iii. wherein the flow sleeve includes aforward portion positioned concentrically within the support sleevebetween the combustion liner and the inner surface of the support sleeveand an aft end that is coupled to the aft frame, the flow sleeveextending continuously between the forward portion of the flow sleeveand the aft frame.
 18. The gas turbine as in claim 17, furthercomprising a cooling flow passage defined between the combustion linerand the flow sleeve that extends continuously between the aft frame andthe forward portion of the flow sleeve.
 19. The gas turbine as in claim17, wherein the combustion liner comprises a conical section and atransition section, the flow sleeve being radially separated from thecombustion liner at a first radial distance with respect to the conicalsection and a second radial distance with respect to the transitionsection.
 20. The gas turbine as in claim 17, wherein the flow sleeve isradially separated from the combustion liner at a radial distance thatvaries along the length of the combustion liner.